Engine Fuctions TRIZ Cases

Stationary sleeve assemblies deliver oil through angled jets to rotating gears, reducing gearbox weight while maintaining reliable lubrication.

Segmented deflector panels absorb technician impact forces and block bird access to cooling surfaces, resolving safety risks and guano accumulation issues.

Movable cascade members expand radially to redirect bypass airflow, reducing engine weight and nacelle length compared to bulky axial systems.

Interference fit connects planet gear parts without welding, preserving carburized surface hardness lost during joint formation.

Fluid injection reduces the coefficient of restitution on outer walls, directing particles into a scavenge passageway instead of the compressor.

A blade shroud protrusion creates vortex flow to separate cooling air from hot gas, reducing mixing losses and improving turbine efficiency.

Severing layer edges before application creates predetermined breaking points that simplify separation and eliminate complex protective conductive layers.

A speed sensor probe mounts axially aft of the compressor hub to detect first spool rotational speed accurately.

A dovetail fixture interlocks with a turbine rotor slot to provide secure mechanical restraint during blade maintenance operations.

A pressure-controlled piston actuator recovers leaked oil from gas turbine engines by blocking outlet openings when system pressure exceeds a threshold.

A hollow arm in a turbofan intermediate casing includes a bypass channel to route hydraulic fluids around a transmission shaft.

A control system applies a transient bias map to adjust variable geometry mechanism position for faster power response.

Fuel heat exchanger preheats natural gas using returned boiler water to raise inlet temperature for the combustor.

Introducing recesses at the blade root adjusts mass distribution to control resonant frequencies in turbine rotor blades.

Introducing oil against the flow direction in an aero engine tank device coalesces small droplets, resolving insufficient separation of fine particles.

Replacing fuel combustion with electric drive eliminates emissions and noise while maintaining reliable jet engine starting capability.

Selective coupling of dual rotating assemblies via a clutch enables versatile power extraction across multiple operational modes.

A rotor balancing system calculates imbalance phase and magnitude to place minimal correction mass.

A purge groove formed by a spar pedestal and coversheet protrusion directs cooling fluid onto the airfoil platform.

An asymmetric inertial shape memory alloy actuator uses gravity for return transitions to prevent accidental movement.

A wind turbine generator system uses a separation device to filter solid particles and liquid drops from intake air before it enters the motor cavity.

Radial piston mechanisms adjust turbine shroud position dynamically, reducing blade strike damage and gas leakage during thermal transients.

A gear cone wall dam redirects oil flow away from teeth while apertures allow controlled fluid exit.

A turbine shroud segment uses a flow constricting slot to link upstream and downstream plenums for enhanced internal cooling.

Segmented exit planes with depressions trap deposits while grill structures direct cooling fluid, preventing plugging and preserving thermal fatigue resistance.

Separate cooling passages in the tip shroud reduce seal rail temperature, preventing creep damage while minimizing system complexity.

A reverse-pass coolant passage directs flow from the trailing edge toward the leading edge within a turbine aerofoil blade.

Tandem generators with variable speed clutches convert kinetic energy at low and high wind speeds without a gearbox.

Centrifugal loading adjusts the engagement load between damper and platform surfaces to mitigate resonance in gas turbine blisks.

A clamping assembly uses a shaft with higher thermal expansion than ceramic matrix composite components to maintain secure coupling.

An accelerator insert reduces cross-sectional area within gas turbine airfoil channels to accelerate airflow and enhance heat transfer.

Circumferential misalignment of concentric airfoils alters natural frequencies to reduce vibratory responses in gas turbine engines.

A modeler predicts turbine output adjustments to coordinate air-fuel control, eliminating feedback delays and overshooting.

Segmented impingement holes meter coolant flow to separate airfoil zones, reducing bleed air extraction while maintaining thermal resistance limits.

Inverting the differential gear configuration so the planet carrier acts as input ensures stable rotation direction for low pressure compressor and fan shafts.

Segmented shroud assembly directs cooling air through internal passages while inter-segment seals prevent leakage across joints to reduce thermal fatigue.

Dynamic adjustment of inlet guide vanes alongside steam injection prevents surge risks while maintaining stable vane loads under varying atmospheric conditions.

Segmented radial and axial passages distribute cooling airflow to reduce thermal loads, extending component operational life.

A buffer memory stores lightning strike parameters to estimate blade damage states using reference values and time-integrated current data.

Optimized vane height to width ratio and tungsten carbide coating manage airflow and resist erosion in turbine nozzle assemblies.

A rotating mist eliminator in a wind turbine rotor head separates water droplets from incoming air to provide dry airflow for generator cooling.

A sensor array uses optical sensors to detect and quantify multiple components of a gaseous fire suppression blend.

Intermediate fillers use perpendicular threaded bores and screws to clamp against channel bases for secure, play-free fixation.

Relocating a stress relief groove to the dovetail bottom side with a widening profile prevents neck portion fretting damage and boosts fatigue life.

A forced air supply system delivers pressurized air to an oil sump via a vent line and inlet.

Vibrating partitions with internal cavities in a honeycomb structure attenuate low frequency sound waves without increasing panel thickness or mass.

Merging support members and oil feed channels into single parts reduces mass and assembly complexity while ensuring reliable bearing lubrication.

Segmented internal cooling circuits direct air to specific blade sections for targeted thermal management.